US8770512B2 - Passive control of ice shedding - Google Patents

Passive control of ice shedding Download PDF

Info

Publication number
US8770512B2
US8770512B2 US13/343,083 US201213343083A US8770512B2 US 8770512 B2 US8770512 B2 US 8770512B2 US 201213343083 A US201213343083 A US 201213343083A US 8770512 B2 US8770512 B2 US 8770512B2
Authority
US
United States
Prior art keywords
wall
engine air
leading edge
air inlet
splitter
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related, expires
Application number
US13/343,083
Other versions
US20120181389A1 (en
Inventor
Robert James Flemming
Eric G. Olsen
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Sikorsky Aircraft Corp
Original Assignee
Sikorsky Aircraft Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Sikorsky Aircraft Corp filed Critical Sikorsky Aircraft Corp
Priority to US13/343,083 priority Critical patent/US8770512B2/en
Assigned to SIKORSKY AIRCRAFT CORPORATION reassignment SIKORSKY AIRCRAFT CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: FLEMMING, ROBERT JAMES, OLSEN, ERIC G.
Publication of US20120181389A1 publication Critical patent/US20120181389A1/en
Application granted granted Critical
Publication of US8770512B2 publication Critical patent/US8770512B2/en
Expired - Fee Related legal-status Critical Current
Adjusted expiration legal-status Critical

Links

Images

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D15/00De-icing or preventing icing on exterior surfaces of aircraft
    • B64D15/16De-icing or preventing icing on exterior surfaces of aircraft by mechanical means
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0233Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising de-icing means

Definitions

  • the subject matter disclosed herein relates to passive control of ice shedding from a helicopter.
  • ice can form on a leading edge of an engine air inlet and can shed during flight. If the pieces of shed ice are large enough, there is a possibility of damage to other helicopter components such as antennas and the tail rotor. Ice may also form on the inner walls of the air inlet duct, whereby shedding may cause flow blockages if, again, the pieces of shed ice are large enough.
  • Active ice protection involves the use of heat or a similar energy source to cause melting or fracturing of accreted ice so that the shed ice does not become large enough to damage antennas or the tail rotor or block the inlet duct.
  • active ice protection also complicates a helicopter design. That is, active controls add to the power requirements, add significant weight and impact reliability and maintainability metrics.
  • a plate includes a body, an aft face at an aft portion of the body, which is attachable to a leading edge of an ice accretion surface such that the body protrudes substantially in a forward direction from the leading edge, and a forward face opposite the aft face, which extends between opposing surfaces of the body and which is oriented substantially perpendicularly with respect to the forward direction and a predominant flow direction of air flowing past the leading edge.
  • a plate is disposed within an engine air inlet of a rotor-machine and includes a retention device coupled to the plate to temporarily hold ice thereto, the retention device including one or more of a straight, curved, bent or looped rod coupled to the plate.
  • a helicopter includes a fuselage including a cabin and a main rotor pylon, an engine air inlet having a leading edge and being coupled to the fuselage proximate to a connection of the main rotor pylon and the cabin and a plate protruding from the leading edge of the engine air inlet and having a forward face, which is oriented substantially perpendicularly with respect to a predominant flow direction of air entering the engine air inlet.
  • an engine air inlet includes an inner wall, an outer wall terminating in a leading edge, which is coupled to the inner wall to define an inlet space extending in an aft direction from the leading edge, a splitter, having a leading edge, disposed within the inlet space between the inner wall and the outer wall and at least one plate protruding in a forward direction from one or more of the respective leading edges of the outer wall and the splitter and having a forward face, which is oriented substantially perpendicularly with respect to the aft and forward directions.
  • FIG. 1 is a perspective view of an engine air inlet
  • FIG. 2 is an enlarged perspective view of a leading edge of the engine air inlet of FIG. 1 ;
  • FIG. 3 is a side view of accreted ice in accordance with embodiments.
  • FIG. 4 is an enlarged view of a retention device in accordance with further embodiments.
  • a passive approach to control the size of shed ice from an aircraft, rotor-machine or rotorcraft, e.g., accreted ice from a helicopter whereby ice is permitted to accrete on forward facing surfaces including a leading edge of an engine air inlet and inlet surfaces that have one or more forward-facing projections.
  • ice on an engine air inlet leading edge can shed as a single piece around the side of the helicopter fuselage and impact other helicopter components such as antennas and tail rotor components. Ice on the leading edge of the engine air inlet can also shed into the inlet, impacting other portions of the inlet including protective screens.
  • installation of one or more plates, fences, splitters or dividers in the area of the ice accretion and substantially aligned with flow streamlines can segment the accreted ice into smaller, less damaging pieces or cause stress concentrations in the ice formation resulting in the fracture of the shed ice before it can impact other parts of the helicopter.
  • one or more straight, curved, bent or looped rods may be provided around which ice can accrete to thereby secure the accreted ice and to prevent the shedding of large ice particles.
  • a helicopter 10 is provided and includes a first fuselage portion 20 defining a cabin and a second fuselage portion 30 defining a main rotor pylon.
  • the cabin is sized and shaped to permit a pilot and, in some cases, additional operators and/or passengers to fit therein.
  • the main rotor pylon is disposed at a top of the cabin and covers components of the main rotor drive system.
  • the first fuselage portion 20 and the second fuselage portion 30 meet and form a shoulder 40 at which an engine air inlet 50 is disposed.
  • the engine air inlet 50 includes an inner wall 60 , an outer wall 70 and, in some cases, a splitter 80 .
  • the inner wall 60 is formed of local segments of the first fuselage portion 20 and the second fuselage portion 30 , such that the inner wall 60 includes a substantially vertical component 61 and a substantially lateral component 62 .
  • the outer wall 70 includes an inner surface and an outer surface that terminate at a common leading edge 71 , which is defined relative to a direction a flow of air into the engine air inlet 50 .
  • the outer wall 70 is coupled to the inner wall 60 to define an inlet space extending in an aft direction from the leading edge 71 .
  • the splitter 80 has a leading edge 81 and is disposed within the inlet space between the inner wall 60 and the outer wall 70 to divide the inlet space and to separate an engine air pathway 82 from a cooling air pathway 83 .
  • the outer wall 70 includes an upper wall 72 , which is substantially aligned with the splitter 80 and the lateral component 62 of the inner wall 60 , a sidewall 73 , which is substantially aligned with the vertical component 61 of the inner wall 60 and a curved corner section 74 to which the upper wall 72 and the sidewall 73 are connected.
  • the leading edge 71 extends over substantially the entire lengths of the upper wall 72 , the sidewall 73 and the curved corner section 74 .
  • the leading edge 81 extends over substantially the entire length of the splitter 80 .
  • each plate 90 protrude from the leading edge of the engine air inlet 50 . That is, each of the one or more plates 90 protrudes from the leading edge 71 and/or the leading edge 81 of the splitter 80 .
  • each plate 90 includes a body 91 , an aft face 92 and a forward face 93 .
  • the aft face 92 is disposed at an aft portion of the body 91 and is attachable to the leading edge 71 or 81 of an ice accretion surface, such as the leading edge of the engine air inlet 50 of a helicopter.
  • the body 91 protrudes substantially in a forward direction from the leading edge 71 or 81 .
  • the forward face 93 faces forwardly from the body 91 , is disposed opposite the aft face 92 and extends between opposing lower and upper surfaces 94 and 95 of the body 91 .
  • the forward face 93 may be oriented substantially perpendicularly with respect to the forward direction and a predominant flow direction of air flowing past the leading edge 71 or 81 along, e.g., the engine air pathway 82 or the cooling air pathway 83 .
  • the one or more of the plates 90 may be disposed along the lengths of the leading edges 71 and 81 and the splitter 80 .
  • the plate 90 may be disposed along the leading edge 71 of the sidewall 73 proximate to or just below the curved corner section 74 .
  • the plate 90 may be aligned in any orientation relative to the horizon but the forward face 93 should be perpendicular to the predominant flow direction of air flowing past the leading edge 71 or 81 along, e.g., the engine air pathway 82 or the cooling air pathway 83 .
  • each plate 90 may have a length, L, measured from the leading edge 71 or 81 that is sufficient to have the plate 90 project from the leading edge 71 or 81 by a distance that is equal to or greater than an expected ice thickness, I.
  • the length, L may be about 3 inches (7.6 cm) with the expected ice thickness, I, equal to, less than or significantly less than that length.
  • a thickness, T, of each plate 90 as measured between the opposing lower and upper surfaces 94 and 95 and at the forward face 93 may be about 0.2 inches (0.5 cm) or more or less. In this way, as shown in FIG. 3 , ice may accrete on the leading edge 71 or 81 and on the forward face 93 .
  • the accreted ice of the leading edge 71 or 81 on either side of the plate 90 will separate from itself and from the accreted ice on the forward face 93 . As such, the accreted ice will not tend to grow large enough (i.e., about 1 lb or more) to cause tail rotor damage or inlet blockage upon shedding.
  • the components of the engine air inlet 50 including the outer wall 70 and the splitter 80 , have airfoil-shaped cross-sections in that each has an increasing thickness as one proceeds along the aft direction from the leading edges 71 and 81 , respectively, until a predefined thickness is reached at which the thickness begins to increase relatively slowly and then stops increasing.
  • the leading edges 71 and 81 may be curved.
  • Each plate 90 may be formed to mimic this curvature although the plate 90 will bulge away from the leading edges 71 and 81 between the aft face 92 and the forward face 93 and may include a rounded leading edge 100 . In alternate embodiments, however, each plate 90 may have a curvature and may further include a sharp leading edge 101 .
  • a retention device 110 may be coupled to an inner duct plate 111 for disposition within a duct formed by the engine air inlet 50 to temporarily hold ice thereto. That is, the retention device 110 prevents or limits the shedding of the ice even where such ice is limited from growing as described above.
  • the retention device 110 may include one or more of a straight rod 112 , a curved or bent rod 113 and/or a looped rod 114 , which are coupled to the inner duct plate 111 by, for example, nut and bolt fasteners.
  • the various rods of the retention device 110 may be arranged in staggered rows and may have varying lengths.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A plate including a body with an aft face at an aft portion of the body, which is attachable to a leading edge of an ice accretion surface such that the body protrudes substantially in a forward direction from the leading edge, and a forward face opposite the aft face, which extends between opposing surfaces of the body and which is oriented substantially perpendicularly with respect to the forward direction and a predominant flow direction of air flowing past the leading edge.

Description

CROSS-REFERENCE TO RELATED APPLICATION
This application claims the benefit of priority to U.S. Provisional Application 61/432,937, which was filed on Jan. 14, 2011 and entitled, “Passive Control of Ice Shedding,” the entire contents of which are incorporated herein by reference.
BACKGROUND OF THE INVENTION
The subject matter disclosed herein relates to passive control of ice shedding from a helicopter.
For certain types of helicopters, ice can form on a leading edge of an engine air inlet and can shed during flight. If the pieces of shed ice are large enough, there is a possibility of damage to other helicopter components such as antennas and the tail rotor. Ice may also form on the inner walls of the air inlet duct, whereby shedding may cause flow blockages if, again, the pieces of shed ice are large enough.
Active ice protection involves the use of heat or a similar energy source to cause melting or fracturing of accreted ice so that the shed ice does not become large enough to damage antennas or the tail rotor or block the inlet duct. Unfortunately, active ice protection also complicates a helicopter design. That is, active controls add to the power requirements, add significant weight and impact reliability and maintainability metrics.
BRIEF DESCRIPTION OF THE INVENTION
According to an aspect of the invention, a plate is provided and includes a body, an aft face at an aft portion of the body, which is attachable to a leading edge of an ice accretion surface such that the body protrudes substantially in a forward direction from the leading edge, and a forward face opposite the aft face, which extends between opposing surfaces of the body and which is oriented substantially perpendicularly with respect to the forward direction and a predominant flow direction of air flowing past the leading edge.
According to another aspect of the invention, a plate is disposed within an engine air inlet of a rotor-machine and includes a retention device coupled to the plate to temporarily hold ice thereto, the retention device including one or more of a straight, curved, bent or looped rod coupled to the plate.
According to another aspect of the invention, a helicopter is provided and includes a fuselage including a cabin and a main rotor pylon, an engine air inlet having a leading edge and being coupled to the fuselage proximate to a connection of the main rotor pylon and the cabin and a plate protruding from the leading edge of the engine air inlet and having a forward face, which is oriented substantially perpendicularly with respect to a predominant flow direction of air entering the engine air inlet.
According to yet another aspect of the invention, an engine air inlet is provided and includes an inner wall, an outer wall terminating in a leading edge, which is coupled to the inner wall to define an inlet space extending in an aft direction from the leading edge, a splitter, having a leading edge, disposed within the inlet space between the inner wall and the outer wall and at least one plate protruding in a forward direction from one or more of the respective leading edges of the outer wall and the splitter and having a forward face, which is oriented substantially perpendicularly with respect to the aft and forward directions.
These and other advantages and features will become more apparent from the following description taken in conjunction with the drawings.
BRIEF DESCRIPTION OF THE DRAWINGS
The subject matter which is regarded as the invention is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features, and advantages of the invention are apparent from the following detailed description taken in conjunction with the accompanying drawings in which:
FIG. 1 is a perspective view of an engine air inlet;
FIG. 2 is an enlarged perspective view of a leading edge of the engine air inlet of FIG. 1;
FIG. 3 is a side view of accreted ice in accordance with embodiments; and
FIG. 4 is an enlarged view of a retention device in accordance with further embodiments.
The detailed description explains embodiments of the invention, together with advantages and features, by way of example with reference to the drawings.
DETAILED DESCRIPTION OF THE INVENTION
With reference to FIGS. 1-4, a passive approach to control the size of shed ice from an aircraft, rotor-machine or rotorcraft, e.g., accreted ice from a helicopter, is provided whereby ice is permitted to accrete on forward facing surfaces including a leading edge of an engine air inlet and inlet surfaces that have one or more forward-facing projections. As mentioned above, ice on an engine air inlet leading edge can shed as a single piece around the side of the helicopter fuselage and impact other helicopter components such as antennas and tail rotor components. Ice on the leading edge of the engine air inlet can also shed into the inlet, impacting other portions of the inlet including protective screens. In accordance with aspects, however, installation of one or more plates, fences, splitters or dividers in the area of the ice accretion and substantially aligned with flow streamlines can segment the accreted ice into smaller, less damaging pieces or cause stress concentrations in the ice formation resulting in the fracture of the shed ice before it can impact other parts of the helicopter. In addition, one or more straight, curved, bent or looped rods may be provided around which ice can accrete to thereby secure the accreted ice and to prevent the shedding of large ice particles.
As shown in FIG. 1, a helicopter 10 is provided and includes a first fuselage portion 20 defining a cabin and a second fuselage portion 30 defining a main rotor pylon. The cabin is sized and shaped to permit a pilot and, in some cases, additional operators and/or passengers to fit therein. The main rotor pylon is disposed at a top of the cabin and covers components of the main rotor drive system. At a confluence of the main rotor pylon and the cabin, the first fuselage portion 20 and the second fuselage portion 30 meet and form a shoulder 40 at which an engine air inlet 50 is disposed.
The engine air inlet 50 includes an inner wall 60, an outer wall 70 and, in some cases, a splitter 80. The inner wall 60 is formed of local segments of the first fuselage portion 20 and the second fuselage portion 30, such that the inner wall 60 includes a substantially vertical component 61 and a substantially lateral component 62. The outer wall 70 includes an inner surface and an outer surface that terminate at a common leading edge 71, which is defined relative to a direction a flow of air into the engine air inlet 50. The outer wall 70 is coupled to the inner wall 60 to define an inlet space extending in an aft direction from the leading edge 71. The splitter 80 has a leading edge 81 and is disposed within the inlet space between the inner wall 60 and the outer wall 70 to divide the inlet space and to separate an engine air pathway 82 from a cooling air pathway 83.
The outer wall 70 includes an upper wall 72, which is substantially aligned with the splitter 80 and the lateral component 62 of the inner wall 60, a sidewall 73, which is substantially aligned with the vertical component 61 of the inner wall 60 and a curved corner section 74 to which the upper wall 72 and the sidewall 73 are connected. The leading edge 71 extends over substantially the entire lengths of the upper wall 72, the sidewall 73 and the curved corner section 74. Similarly, the leading edge 81 extends over substantially the entire length of the splitter 80.
At least one ore more plates 90 protrude from the leading edge of the engine air inlet 50. That is, each of the one or more plates 90 protrudes from the leading edge 71 and/or the leading edge 81 of the splitter 80. As shown in FIGS. 2 and 3, each plate 90 includes a body 91, an aft face 92 and a forward face 93. The aft face 92 is disposed at an aft portion of the body 91 and is attachable to the leading edge 71 or 81 of an ice accretion surface, such as the leading edge of the engine air inlet 50 of a helicopter. By way of the attachment, the body 91 protrudes substantially in a forward direction from the leading edge 71 or 81. The forward face 93 faces forwardly from the body 91, is disposed opposite the aft face 92 and extends between opposing lower and upper surfaces 94 and 95 of the body 91. In accordance with embodiments, the forward face 93 may be oriented substantially perpendicularly with respect to the forward direction and a predominant flow direction of air flowing past the leading edge 71 or 81 along, e.g., the engine air pathway 82 or the cooling air pathway 83.
The one or more of the plates 90 may be disposed along the lengths of the leading edges 71 and 81 and the splitter 80. In a particular exemplary embodiment, the plate 90 may be disposed along the leading edge 71 of the sidewall 73 proximate to or just below the curved corner section 74. In any case, the plate 90 may be aligned in any orientation relative to the horizon but the forward face 93 should be perpendicular to the predominant flow direction of air flowing past the leading edge 71 or 81 along, e.g., the engine air pathway 82 or the cooling air pathway 83.
In accordance with embodiments, each plate 90 may have a length, L, measured from the leading edge 71 or 81 that is sufficient to have the plate 90 project from the leading edge 71 or 81 by a distance that is equal to or greater than an expected ice thickness, I. For example, the length, L, may be about 3 inches (7.6 cm) with the expected ice thickness, I, equal to, less than or significantly less than that length. A thickness, T, of each plate 90 as measured between the opposing lower and upper surfaces 94 and 95 and at the forward face 93 may be about 0.2 inches (0.5 cm) or more or less. In this way, as shown in FIG. 3, ice may accrete on the leading edge 71 or 81 and on the forward face 93. However, at the plate 90, the accreted ice of the leading edge 71 or 81 on either side of the plate 90 will separate from itself and from the accreted ice on the forward face 93. As such, the accreted ice will not tend to grow large enough (i.e., about 1 lb or more) to cause tail rotor damage or inlet blockage upon shedding.
The components of the engine air inlet 50, including the outer wall 70 and the splitter 80, have airfoil-shaped cross-sections in that each has an increasing thickness as one proceeds along the aft direction from the leading edges 71 and 81, respectively, until a predefined thickness is reached at which the thickness begins to increase relatively slowly and then stops increasing. Thus, the leading edges 71 and 81 may be curved. Each plate 90 may be formed to mimic this curvature although the plate 90 will bulge away from the leading edges 71 and 81 between the aft face 92 and the forward face 93 and may include a rounded leading edge 100. In alternate embodiments, however, each plate 90 may have a curvature and may further include a sharp leading edge 101.
With reference to FIG. 4, a retention device 110 may be coupled to an inner duct plate 111 for disposition within a duct formed by the engine air inlet 50 to temporarily hold ice thereto. That is, the retention device 110 prevents or limits the shedding of the ice even where such ice is limited from growing as described above. The retention device 110 may include one or more of a straight rod 112, a curved or bent rod 113 and/or a looped rod 114, which are coupled to the inner duct plate 111 by, for example, nut and bolt fasteners. The various rods of the retention device 110 may be arranged in staggered rows and may have varying lengths.
While the invention has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the invention is not limited to such disclosed embodiments. Rather, the invention can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the invention. Additionally, while various embodiments of the invention have been described, it is to be understood that aspects of the invention may include only some of the described embodiments. Accordingly, the invention is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.

Claims (9)

The invention claimed is:
1. An engine air inlet, comprising:
an inner wall;
an outer wall terminating in a leading edge, which is coupled to the inner wall to define an inlet space extending in an aft direction from the leading edge;
a splitter, having a leading edge, disposed within the inlet space between the inner wall and the outer wall; and
at least one plate protruding in a forward direction from one or more of the respective leading edges of the outer wall and the splitter and having a forward face, which is oriented substantially perpendicularly with respect to the aft and forward directions.
2. The engine air inlet according to claim 1, wherein the inner wall has substantially lateral and vertical components and the outer wall comprises:
an upper wall substantially aligned with the splitter and the inner wall lateral component;
a sidewall substantially aligned with the inner wall vertical component; and
a curved corner section at which the upper wall and the sidewall meet.
3. The engine air inlet according to claim 2, wherein the at least one plate protrudes from the respective leading edges of the outer wall at the upper wall, the sidewall and the corner section and the splitter.
4. The engine air inlet according to claim 2, wherein the at least one plate protrudes from the leading edge of the sidewall proximate to the curved corner section.
5. The engine air inlet according to claim 1, wherein the splitter divides the inlet space to separate an engine air pathway from a cooling air pathway.
6. The engine air inlet according to claim 1, wherein the respective leading edges of the outer wall and the splitter have airfoil-shaped cross-sections.
7. The engine air inlet according to claim 6, wherein a cross-section of the plate mimics the airfoil-shaped cross-section of the leading edges.
8. The engine air inlet according to claim 1, wherein the forward face has one of a rounded leading edge and a sharp leading edge.
9. The engine air inlet according to claim 1, further comprising a retention device coupled to an inner duct plate disposed within the inlet space to temporarily hold ice thereto, the retention device comprising one or more of a straight, curved, bent, or looped rod coupled to the plate.
US13/343,083 2011-01-14 2012-01-04 Passive control of ice shedding Expired - Fee Related US8770512B2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US13/343,083 US8770512B2 (en) 2011-01-14 2012-01-04 Passive control of ice shedding

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201161432937P 2011-01-14 2011-01-14
US13/343,083 US8770512B2 (en) 2011-01-14 2012-01-04 Passive control of ice shedding

Publications (2)

Publication Number Publication Date
US20120181389A1 US20120181389A1 (en) 2012-07-19
US8770512B2 true US8770512B2 (en) 2014-07-08

Family

ID=45491423

Family Applications (1)

Application Number Title Priority Date Filing Date
US13/343,083 Expired - Fee Related US8770512B2 (en) 2011-01-14 2012-01-04 Passive control of ice shedding

Country Status (2)

Country Link
US (1) US8770512B2 (en)
EP (1) EP2476617B1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11492923B2 (en) * 2018-04-09 2022-11-08 Gulfstream Aerospace Corporation Ice shedding aircraft engine

Citations (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2504684A (en) 1946-01-30 1950-04-18 Goodrich Co B F Extensible structure for varying the configuration of an aircraft surface
US2970794A (en) 1957-05-24 1961-02-07 Herbert C Johnson Inflatable de-icing boot
US3794444A (en) 1971-10-04 1974-02-26 Gen Electric Anti-icing spinner construction
US4494715A (en) 1983-05-09 1985-01-22 The B. F. Goodrich Company Deicer
US4613102A (en) 1985-02-21 1986-09-23 The B. F. Goodrich Company Pneumatic deicers with template
US4706911A (en) 1986-01-27 1987-11-17 Briscoe James A Method and apparatus for deicing a leading edge
US4776755A (en) * 1986-03-27 1988-10-11 Wartsila Meriteollisuus Oy Shrouded propeller
US4836474A (en) 1987-07-16 1989-06-06 The B. F. Goodrich Company De-icer
US4852343A (en) 1987-07-02 1989-08-01 Avco Corporation Method of operating anti-icing valve
US5014606A (en) 1987-11-23 1991-05-14 Steiner Norman F Windshield defroster system for the Bell Helicopter Textron, Inc., model 206 helicopter and military derivatives
US5182944A (en) 1991-01-18 1993-02-02 Brunnenkant Siegfried W Helicopter icing spray system
US5490644A (en) * 1993-12-20 1996-02-13 The Boeing Company Ducted boundary layer diverter
US5553814A (en) 1992-12-30 1996-09-10 The B.F. Goodrich Company Skin for a deicer
US5752674A (en) 1996-08-21 1998-05-19 General Electric Company Sensor ice shield
US6250588B1 (en) 1999-07-27 2001-06-26 The United States Of America As Represented By The Secretary Of The Air Force Forced air de-icing and washing system attached to the distal end of a boom
US20040194627A1 (en) 2003-04-04 2004-10-07 United Technologies Corporation System and method for thermal management
US6848652B2 (en) 2003-02-28 2005-02-01 Sikorsky Aircraft Corporation Aircraft heater
WO2006107741A2 (en) 2005-04-06 2006-10-12 Sikorsky Aircraft Corporation Dual-channel deicing system for a rotary wing aircraft
WO2006113388A2 (en) 2005-04-13 2006-10-26 Sikorsky Aircraft Corporation Integrated engine air particle filter assembly
US7131815B2 (en) 2003-07-11 2006-11-07 Rolls-Royce Plc Inlet guide vane
US7594627B2 (en) 2004-11-19 2009-09-29 Chinook Mobile Heating And Deicing Corporation Method and apparatus for de-icing aircraft and other snow or ice covered surfaces
US20090272850A1 (en) 2008-04-30 2009-11-05 General Electric Company Ice shed reduction for leading edge structures
US20100096507A1 (en) 2008-07-29 2010-04-22 Markus Villinger Heating device for deicing aircraft parts
US20100101206A1 (en) 2007-03-19 2010-04-29 Turbomeca Device for de-icing the air intake of a gas turbine
US20100108814A1 (en) 2008-11-03 2010-05-06 Etling Keith A Anti-icing apparatus for honeycomb structures
US20100163678A1 (en) 2007-03-06 2010-07-01 Karl Gregory Thermal anti-icing system
EP2399828A1 (en) 2010-06-24 2011-12-28 Eurocopter Method for preventing the clogging of a grating, grating and air intake implementing such a method

Patent Citations (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2504684A (en) 1946-01-30 1950-04-18 Goodrich Co B F Extensible structure for varying the configuration of an aircraft surface
US2970794A (en) 1957-05-24 1961-02-07 Herbert C Johnson Inflatable de-icing boot
US3794444A (en) 1971-10-04 1974-02-26 Gen Electric Anti-icing spinner construction
US4494715A (en) 1983-05-09 1985-01-22 The B. F. Goodrich Company Deicer
US4613102A (en) 1985-02-21 1986-09-23 The B. F. Goodrich Company Pneumatic deicers with template
US4706911A (en) 1986-01-27 1987-11-17 Briscoe James A Method and apparatus for deicing a leading edge
US4776755A (en) * 1986-03-27 1988-10-11 Wartsila Meriteollisuus Oy Shrouded propeller
US4852343A (en) 1987-07-02 1989-08-01 Avco Corporation Method of operating anti-icing valve
US4836474A (en) 1987-07-16 1989-06-06 The B. F. Goodrich Company De-icer
US5014606A (en) 1987-11-23 1991-05-14 Steiner Norman F Windshield defroster system for the Bell Helicopter Textron, Inc., model 206 helicopter and military derivatives
US5182944A (en) 1991-01-18 1993-02-02 Brunnenkant Siegfried W Helicopter icing spray system
US5553814A (en) 1992-12-30 1996-09-10 The B.F. Goodrich Company Skin for a deicer
US5490644A (en) * 1993-12-20 1996-02-13 The Boeing Company Ducted boundary layer diverter
US5752674A (en) 1996-08-21 1998-05-19 General Electric Company Sensor ice shield
US6250588B1 (en) 1999-07-27 2001-06-26 The United States Of America As Represented By The Secretary Of The Air Force Forced air de-icing and washing system attached to the distal end of a boom
US6848652B2 (en) 2003-02-28 2005-02-01 Sikorsky Aircraft Corporation Aircraft heater
US6939392B2 (en) 2003-04-04 2005-09-06 United Technologies Corporation System and method for thermal management
US20040194627A1 (en) 2003-04-04 2004-10-07 United Technologies Corporation System and method for thermal management
US7131815B2 (en) 2003-07-11 2006-11-07 Rolls-Royce Plc Inlet guide vane
US7594627B2 (en) 2004-11-19 2009-09-29 Chinook Mobile Heating And Deicing Corporation Method and apparatus for de-icing aircraft and other snow or ice covered surfaces
WO2006107741A2 (en) 2005-04-06 2006-10-12 Sikorsky Aircraft Corporation Dual-channel deicing system for a rotary wing aircraft
US20060226292A1 (en) 2005-04-06 2006-10-12 Sikorsky Aircraft Corporation Dual-channel deicing system for a rotary wing aircraft
WO2006113388A2 (en) 2005-04-13 2006-10-26 Sikorsky Aircraft Corporation Integrated engine air particle filter assembly
US20100163678A1 (en) 2007-03-06 2010-07-01 Karl Gregory Thermal anti-icing system
US20100101206A1 (en) 2007-03-19 2010-04-29 Turbomeca Device for de-icing the air intake of a gas turbine
US20090272850A1 (en) 2008-04-30 2009-11-05 General Electric Company Ice shed reduction for leading edge structures
US20100096507A1 (en) 2008-07-29 2010-04-22 Markus Villinger Heating device for deicing aircraft parts
US20100108814A1 (en) 2008-11-03 2010-05-06 Etling Keith A Anti-icing apparatus for honeycomb structures
EP2399828A1 (en) 2010-06-24 2011-12-28 Eurocopter Method for preventing the clogging of a grating, grating and air intake implementing such a method

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
European Search Report; European Application No. 12151140.6-2422; European Filing Date: Apr. 11, 2012; Date of mailing: Apr. 12, 2012.

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11492923B2 (en) * 2018-04-09 2022-11-08 Gulfstream Aerospace Corporation Ice shedding aircraft engine

Also Published As

Publication number Publication date
EP2476617A1 (en) 2012-07-18
US20120181389A1 (en) 2012-07-19
EP2476617B1 (en) 2014-07-16

Similar Documents

Publication Publication Date Title
US9567062B2 (en) Box wing with angled gas turbine engine cores
US8622342B2 (en) On-board aircraft auxiliary power systems having dual auxiliary power units
US8191823B2 (en) Mast having modifiable geometry for securing an engine to an aircraft wing
US10336458B2 (en) Aircraft assembly comprising a mounting strut built into the nacelle and arranged at the rear section of the fuselage
RU2608983C2 (en) Aircraft with fuselage engines and inner screen
US8960603B2 (en) Impact resistant and damage tolerant aircraft fuselage
US20140130512A1 (en) Turbine engine attachment structure
US20090212165A1 (en) Passive removal of suction air for laminar flow control, and associated systems and methods
US8579231B2 (en) Method of manufacture by superplastic forming and by fishplating of a rib for an aerodynamic fairing of an aircraft engine mounting pylon
US20140054413A1 (en) Airplane having a rear propulsion system
US10562641B2 (en) AFT exhaust system for rotary wing aircraft
US8322981B2 (en) Aircraft fluid diversion inlet louver
CN105083565B (en) Propulsion assembly and aircraft for aircraft
US20150314883A1 (en) Intake for an Engine of an Aircraft
US9499276B2 (en) Helicopter with engine air intakes
US8157204B2 (en) Double fuselage aircraft
US8770512B2 (en) Passive control of ice shedding
US9868539B2 (en) Aircraft engine pylon to wing mounting assembly
US20160229544A1 (en) Ice accretion prevention
EP3372507B1 (en) Air intake assembly with horizontal door for an aircraft auxiliary power unit
US9108714B2 (en) Under-flap stiffener for aircraft
US11634228B2 (en) High volume flow management of cooling air
US20160176501A1 (en) Device for protecting the front spar structure of a central casing of an aircraft wing and at least one piece of equipment located in said wing
US20160068270A1 (en) Air generation unit for an aircraft
CN206125397U (en) Can throw flap

Legal Events

Date Code Title Description
AS Assignment

Owner name: SIKORSKY AIRCRAFT CORPORATION, CONNECTICUT

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:FLEMMING, ROBERT JAMES;OLSEN, ERIC G.;SIGNING DATES FROM 20101110 TO 20101118;REEL/FRAME:027475/0242

STCF Information on status: patent grant

Free format text: PATENTED CASE

MAFP Maintenance fee payment

Free format text: PAYMENT OF MAINTENANCE FEE, 4TH YEAR, LARGE ENTITY (ORIGINAL EVENT CODE: M1551)

Year of fee payment: 4

FEPP Fee payment procedure

Free format text: MAINTENANCE FEE REMINDER MAILED (ORIGINAL EVENT CODE: REM.); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY

LAPS Lapse for failure to pay maintenance fees

Free format text: PATENT EXPIRED FOR FAILURE TO PAY MAINTENANCE FEES (ORIGINAL EVENT CODE: EXP.); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY

STCH Information on status: patent discontinuation

Free format text: PATENT EXPIRED DUE TO NONPAYMENT OF MAINTENANCE FEES UNDER 37 CFR 1.362

FP Lapsed due to failure to pay maintenance fee

Effective date: 20220708